Electric Propeller Reverse Thrust for Wing Slipstream Attitude Control
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Solution Overview
Problem
Existing methods for generating aerodynamic forces in aircraft using propeller slipstreams result in excessive energy input, impaired fuel consumption, and unintended aerodynamic forces, and fail to distribute lift effectively to protect the main wing structure from wind gusts.
Innovation Solution
An electric aircraft equipped with a first electric propulsion system, including a propeller and motor, allows for adjusting thrust to negative values through regeneration or reverse rotation, distributing propulsion systems to generate aerodynamic forces efficiently without impacting fuel consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If the slipstream accelerated by the propeller is used to generate aerodynamic force on the wing, then the lift is increased, but the energy input to the propeller becomes excessively larger than required for normal flight
Solution Approach 1:
The patent applies reverse thrust by rotating the propeller in the opposite direction to create negative thrust. This inverted action allows the aircraft to generate aerodynamic forces for attitude control without requiring excessive positive thrust input, thereby resolving the energy consumption problem while maintaining the ability to generate necessary aerodynamic forces.
Solution Approach 2:
The patent changes the thrust parameter from positive to negative by reversing propeller rotation. This parameter change enables the system to generate aerodynamic forces for attitude control without the excessive energy input required by traditional methods that rely solely on increased positive thrust.
2Force
If the slipstream accelerated by the propeller is used to generate aerodynamic force, then the lift is increased, but fuel consumption performance is impaired
Solution Approach 1:
By using reverse thrust instead of excessive positive thrust, the system generates necessary aerodynamic forces for attitude control without the fuel consumption penalty. The inverted propeller rotation creates negative thrust that efficiently produces the required aerodynamic effects while maintaining fuel economy.
3Force
If the existing control surface is operated to reduce main wing load, then the aerodynamic force is adjusted, but the distribution of lift of the main wing cannot be changed to protect the main wing structure
Solution Approach 1:
The patent segments the thrust control by using multiple propellers positioned at different locations on the aircraft. This segmentation enables independent control of lift distribution across different wing sections, allowing the system to protect the main wing structure from wind gusts by adjusting local lift distribution rather than uniformly adjusting the entire wing's aerodynamic force.
Solution Approach 2:
The patent applies local quality control by positioning propellers at specific locations to create localized aerodynamic effects. This allows differential lift distribution across the wing span, enabling targeted protection of the main wing structure from wind gusts while maintaining overall flight stability.
4Reliability
If conventional aerodynamic devices and actuators are used for automated operation, then the safety is improved, but the cost becomes enormous
Solution Approach 1:
The patent makes the propeller system multi-functional by using it for both propulsion and attitude control. This eliminates the need for separate conventional aerodynamic devices and actuators, significantly reducing system complexity and cost while maintaining automated operation capability and safety through the same propulsion system.
Solution Approach 2:
The patent merges the propulsion system and attitude control system into a single integrated system. By combining these functions, the patent eliminates redundant components such as separate actuators and control computers, thereby reducing cost and device complexity while maintaining the safety benefits of automated operation.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The system generates aerodynamic forces in proportionate amounts, reduces fuel consumption, and effectively distributes lift, enabling efficient attitude control and protection against wind gusts while maintaining low cost and high reliability.
Implementation Method 1
a first electric propulsion system including a first propeller or fan for propulsion and a first electric motor that drives the first propeller or fan
Implementation Method 2
a first electric propulsion system including a first propeller or fan for propulsion
Data Source
AI summary
[Object] To provide an electric aircraft and an attitude control method therefor that are capable of generating an aerodynamic force in just proportions without impairing fuel consumption performance.[Solving Means] In an electric aircraft 1, an electric propulsion system 20 including a propeller 21 for propulsion and an electric motor 22 that drives the propeller 21 for propulsion is disposed at a leading edge of a wing 10 such that the slipstream generated by the electric propulsion system 20 acts on the wing 10. A controller 30 is capable of adjusting a thrust of the electric propulsion system 20 to a negative value.